2020-06-12: Main Rotor Gearbox

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): \n\n2020-06-12 Airbus Helicopters: Amendment 39-19881; Docket No. FAA- 2018-0019; Product Identifier 2017-SW-074-AD. \n\n(a) Applicability \n\n\n\tThis AD applies to Airbus Helicopters Model AS332L2 and EC225LP helicopters, certificated in any category, with a main gearbox (MGB) suspension bar front attachment bolt (bolt) part number (P/N) 332A22-1613-21 or 332A22-1613-20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB suspension bar front attachment fitting (fitting) P/N 332A22-1623-01, MGB suspension bar rear left hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar rear right hand fitting P/N 332A22-1624-03 or 332A22-1624-05 installed. \n\n(b) Unsafe Condition \n\n\n\tThis AD defines the unsafe condition as MGB suspension bar bolts and fittings remaining in service beyond their fatigue life and loose MGB suspension bar bolts or fittings, which could result in structural failure of the MGB suspension bar and loss of helicopter control. \n\n(c) Effective Date \n\n\n\tThis AD becomes effective May 11, 2020. \n\n(d) Compliance \n\n\n\tYou are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. \n\n(e) Required Actions \n\n\n\t(1) Within 30 hours time-in-service (TIS), review records to determine the total hours TIS of each MGB suspension bar bolt. \n\t(i) Determine the life limit of each bolt by applying the hours TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 01.00.86, Revision 1, dated August 25, 2017 (EASB 01.00.86), or Airbus Helicopters Emergency Alert Service Bulletin No. 04A013, Revision 1, dated August 25, 2017, as applicable to your model helicopter. \n\tNote 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters refers to bolts as ''pins.'' \n\t(A) Before further flight, remove from service any bolt that has reached or exceeded its life limit. \n\t(B) For each bolt that has not exceeded its life limit, continue to calculate and record the life limit on its component history card or equivalent record by applying the add-on factor each time the helicopter accumulates hours TIS, and remove from service any bolt before reaching its life limit. \n\t(ii) Thereafter following paragraph (e)(1)(i) of this AD, continue to calculate and record the life limit of each bolt on its component history card or equivalent record by applying the add-on factor each time the helicopter accumulates hours TIS and remove from service any bolt before reaching its life limit. \n\t(2) For Model AS332L2 helicopters, within 30 hours TIS, review records to determine the total hours TIS of each MGB suspension bar fitting. \n\t(i) Determine the life limit of each fitting by applying the hours TIS by the add-on factor listed in Table No. 1 of EASB 01.00.86. \n\t(A) Before further flight, remove from service any fitting that has reached or exceeded its life limit. \n\t(B) For each fitting that has not exceeded its life limit, continue to calculate and record the life limit on its component history card or equivalent record by applying the add-on factor each time the helicopter accumulates hours TIS, and remove from service any fitting before reaching its life limit. \n\t(ii) Thereafter following paragraph (e)(2)(i) of this AD, continue to calculate and record the life limit of each fitting on its component history card or equivalent record by applying the add- on factor each time the helicopter accumulates hours TIS and remove from service any fitting before reaching its life limit. \n\t(3) For Model AS332L2 helicopters, within 150 hours TIS (without the add-on factor), inspect the torque of each MGB suspension bar attachment front and rear nut. The allowable torque for each front nut is 602-663 lbf. in (6.8-7.5 daN.m) and the allowable torque for each rear nut is 337-398 lbf. in (3.8-4.5 daN.m). \n\t(i) If the torque on any nut is higher than the maximum allowable torque stated in paragraph (e)(3) of this AD, before further flight, remove from service the bolt and nut. \n\t(ii) If the torque on any nut is lower than the minimum allowable torque value stated in paragraph (e)(3) of this AD, before further flight, tighten the nut to the allowable torque stated in paragraph (e)(3) of this AD. Within 150 hours TIS (without the add- on factor), remove from service any bolt and nut that were tightened as required by this paragraph. \n\n(f) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 \n\n((Page 19080)) \n\nHillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. \n\t(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. \n\n(g) Additional Information \n\n\n\tThe subject of this AD is addressed in European Union Aviation Safety Agency (previously European Aviation Safety Agency) (EASA) AD No. 2017-0189, dated September 22, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2018- 0019.(h) Subject \n\n\n\tJoint Aircraft Service Component (JASC) Code: 6320, Main Rotor Gearbox. \n\n(i) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 01.00.86, Revision 1, dated August 25, 2017. \n\t(ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated August 25, 2017. \n\t(3) For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. \n\t(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817-222-5110. \n\t(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on March 25, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-07140 Filed 4-3-20; 8:45 am) BILLING CODE 4910-13-P